Combustor for a gas-turbine engine with angled pilot fuel nozzle
AssigneeSiemens Aktiengesellschaft
InventorNigel Wilbraham
Life of this patent
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Abstract
A combustor for a gas-turbine engine including a burner head, a combustion chamber disposed downstream of the burner head, a swirler for creating a swirling flow of air in the combustion chamber, and a fuel nozzle disposed in the burner head. The fuel nozzle is disposed giving rise to a first angle of exit of the fuel from a downstream face of the burner head of >±0° with respect to a longitudinal axis of the combustor, this first angle lying in a first plane passing through the longitudinal axis. The fuel also exits at a second angle from the downstream face of >±0° with respect to the first plane, the second angle lying in a second plane orthogonal to the first plane.
Claims16
A combustor for a gas-turbine engine, comprising:
- a burner head;
- a combustion chamber disposed downstream of the burner head;
- a swirler for creating a swirling flow of air in the combustion chamber;
- and
- a plurality of fuel nozzles disposed in the burner head for supplying fuel to the combustion chamber,
- wherein each of the plurality of fuel nozzles is disposed in the burner head such as to give rise to a first angle of exit of the fuel from a downstream face of the burner head with respect to a longitudinal axis of the combustor, the first angle being unequal to 0° such that the fuel nozzle is tilted toward the longitudinal axis,
- wherein the first angle lies in a first plane passing through the longitudinal axis,
- wherein each of said plurality of fuel nozzles is disposed in the burner head such as to also give rise to a second angle of exit of the fuel from the downstream face with respect to the first plane, the second angle being greater than or less than 0°, and
- wherein the second angle lies in a second plane orthogonal to said first plane, and
- wherein the first angle and second angle varies between individual fuel nozzles of the plurality of fuel nozzles or between groups of said plurality of fuel nozzles.
A combustor for a gas-turbine engine, comprising:
- a burner head;
- a combustion chamber disposed downstream of the burner head;
- a swirler for creating a swirling flow of air in the combustion chamber;
- and
- a plurality of fuel nozzles disposed in the burner head for supplying fuel to the combustion chamber,
- wherein each of the plurality of fuel nozzles is disposed in the burner head such as to give rise to a first angle of exit of the fuel from a downstream face of the burner head with respect to a longitudinal axis of the combustor, the first angle being unequal to 0°,
- wherein the first angle lies in a first plane passing through the longitudinal axis,
- wherein each of said plurality of fuel nozzles is disposed in the burner head such as to also give rise to a second angle of exit of the fuel from the downstream face with respect to the first plane, the second angle being unequal to 0°,
- wherein the second angle lies in a second plane orthogonal to said first plane,
- wherein individual fuel nozzles of the plurality of fuel nozzles have different first angles and different second angles,
- wherein at least one of the plurality of fuel nozzles is a pilot fuel nozzle supplying only pilot fuel to the combustion chamber, the pilot fuel nozzle being disposed off-center with respect to the longitudinal axis, and
- wherein the first angle is configured so as to direct pilot fuel from the pilot fuel nozzle toward the longitudinal axis.
Dependencies are inferred from the claim text.